NACA-RM-L53H31 REV A

Abstract

INTRODUCTION <br>It was shown in reference 1 that near the speed of sound, the zero- 1 lift drag rise for a thin low-aspect-ratio wing-body combination is primarily dependent on the axial distribution of cross-section area normal to the airstream. Also, it was found that contouring the bodies of wing-body combinations to obtain improved axial distributions of cross-sectional area for the combinations results in substantial reductions in the drag-rise increments at transonic speeds. <br>More recently, by considering the physical nature of the flow at moderate supersonic speeds, a concept has been developed which should interrelate- qualitatively the zero-lift wave drag tions at these speeds w i t h axial distributions of of wing-body combinations at these speeds with distributions of cross-sectional areas. On the basis of this concept and other design procedures, a structurally feasible swept-wing indented-body combination has been designed to have significantly improved lift-to-drag ratios over a range of transonic and moderate supersonic mach numbers. <br>Although, at the present time, experimental results have been obtained for this wing-body configuration for only the lower portion of design speed range (mach numbers up to 1.15), the favorable nature of together with the development of the supersonic area rule and the considerations involved in the design, before experimental results for the complete design speed range have been obtained.